CN106435432A - Thermal barrier coating with controllable porosity and pore morphology and preparation method of thermal barrier coating - Google Patents
Thermal barrier coating with controllable porosity and pore morphology and preparation method of thermal barrier coating Download PDFInfo
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Abstract
The invention provides a thermal barrier coating with controllable porosity and pore morphology and a preparation method of the thermal barrier coating and belongs to the technical field of materials. Firstly, composite powder containing a thermal barrier coating ceramic material and pore-forming materials in different forms is prepared, a composite coating with the volume fraction of the pore-forming materials being 5%-50% is prepared in a deposition manner through a thermal spraying method, the pore-forming materials are free of deformation in the thermal spraying process, and the original morphology is kept. The pore-forming materials in the composite coating are burnt off in an oxidization manner, and therefore pores same as the pore-forming materials in morphology and position are obtained in the coating. Compared with a traditional thermal barrier coating, the porosity and the pore morphology of the thermal barrier coating prepared through the method are controllable, the pores are free of sintering in the service and use of the coating, and by adjusting the porosity and the pore morphology, the service performance and the service stability of the thermal barrier coating can be substantially improved.
Description
Technical field
The invention belongs to field of material technology and in particular to a kind of porosity and the controlled thermal barrier coating of pore appearance and its
Preparation method.
Background technology
The development of the industries such as Aero-Space, energy source and power proposes higher wanting to aero-engine and industry gas turbine
Ask it is desirable to hot-end component carries out long service under conditions of high temperature, corrosion, wear, this is directly to gas turbine hot-end component
Surface property put forward higher requirement it is necessary to using cooling and provision for thermal insulation, guarantee turbine blade is in high temperature ring
Work for a long time in border.The cooling technology commonly used at present mainly has three kinds：Cooling air-flow cooling technology within turbine blade,
Air film cooling technology and Thermal Barrier Coating Technologies.The development of Thermal Barrier Coating Technologies make the temperature on turbine blade surface reduce 100～
300℃.
Thermal spraying thermal barrier coating has the characteristics such as heat-proof quality is high, thermal strain mitigation ability is strong, thus being widely used as aviation
The thermal barrier coating on the hot-end component such as electromotor and gas turbine surface, protects high temperature by modes such as high temperature insulating, Anti-erosions
Alloy component, realizes improving whole machine fuel availability and extends the targets such as machine life.
Thermal Barrier Coating Layers Prepared By Plasma Spraying has 5%～15% hole：Spherical pore, flaky particles internal longitudinal bore gap, flat grain
Horizontal hole etc. between son.Research shows, porosity and pore structure have appreciable impact to the thermal conductivity of coating and mechanical property.
Low thermal conductivity can reduce metallic matrix temperature, reduces the burden of cooling system, and low elastic modelling quantity can reduce thermal cycle
During the thermal strain that produces, high fracture toughness can improve the resistance of cracks can spread.Applied by the structure adjusting coating
Layer thickness direction preparation structure Thermal Barrier Coatings are to improve the effective ways of thermal barrier coating thermal cycle life.
Traditional thermal spraying thermal barrier coating generally reaches different porositys, this coating porosity by adjusting spray parameters
Rate modification scope is less, and the pattern of uncontrollable coating inner pore.Formed generally between flaky particles significantly reduces heat
The flat hole of conductivity, because gap is typically smaller than 100nm, and when being on active service under the hot conditionss higher than more than 1000 DEG C, sends out
Raw quick healing is it is impossible to maintain stable low-thermal conductivity, the characteristic of low elastic modulus.If it is possible to development is more significantly
The porosity of degree adjustment coating simultaneously regulates and controls pore appearance and size, not only can effectively reduce pyroconductivity and elastic modelling quantity, and
There is not the method for the hole of sintering that heals under the conditions of applied at elevated temperature, to the performance tool weight improving thermal spraying heat barrier ceramic coating
Want meaning, provide wider selection for design many ceramic layer structures thermal barrier coating simultaneously.
Content of the invention
For the defect overcoming above-mentioned prior art to exist, it is an object of the invention to provide a kind of porosity and hole shape
Controlled thermal barrier coating of looks and preparation method thereof, the method can significantly adjust the porosity of coating, and regulates and controls coating endoporus
The pattern of gap and size, make the hole of formation that the thermal conductivity of coating be greatly lowered in thermal barrier coating use, elastic modelling quantity, with
When these holes structure do not change at a temperature of high-temperature service environment with size, thus for the excellent many knots of design performance
The ceramic heat-barrier coating of structure hole provides effective solution.
The present invention is to be achieved through the following technical solutions：
The invention discloses the preparation method of a kind of porosity and the controlled thermal barrier coating of pore appearance, walk including following
Suddenly：
1) pass through spray drying method, prepare the composite powder containing thermal barrier coating ceramic material and pore forming material, pore-creating material
Volume fraction in composite powder for the material is 5%～50%；
Wherein, pore forming material is subsphaeroidal particle or 10～50 μm of length, 0.3～10 μm of the width of 5～50 μm of diameter
One of flat material particle or two kinds；
2) pass through hot spray process, the composite powder comprising thermal barrier coating ceramic material and pore forming material is deposited on matrix
On；
Wherein, during the deposition of the composite powder containing subsphaeroidal pore forming material, the subsphaeroidal form of pore forming material keeps constant；
And the pore-creating particle in the compound particle containing flat pore-creating particle, send out with the ceramic particle part of heating fusing in deposition
Raw flattening, thus forming length along flat directional spreding in flat ceramic particle to be 10～50 μm, width is 0.3～10 μm
Flat particle；
3) pass through high-temperature oxidation, the pore forming material in burn off composite coating, obtain in the coating and pore forming material pattern
And position identical hole, that is, porosity and pore appearance controlled thermal barrier coating are obtained.
Described pore forming material is the carbon simple substance that can be removed by high-temperature oxidation or high-melting-point Organic substance.
Pore forming material is graphite or activated carbon.
Thermal barrier coating ceramic material is zirconic acid lanthanum (La2Zr2O7), lanthanum cerate (La2Ce2O7), gadolinium zirconate (Gd2Zr2O7), six
Lanthanum aluminate, aluminium oxide, yttria-stabilized zirconia (YSZ) or the zirconium oxide containing other steady oxides, or other can be used as
The ceramic material of heat barrier ceramic coating.
When containing two kinds of pore forming material, with the composite powder containing subsphaeroidal pore forming material and containing flat pore-creating simultaneously
After the composite powder of material mixes in varing proportions, form hot spray powder；Any of which of two kinds of composite powders is in heat
Ratio in dusty spray is 0～100%.
Step 2) described hot spray process adopt plasma spraying or plasma spraying complex phase deposition.
Step 3) described high-temperature oxidation is to put into the composite powder comprising thermal barrier coating ceramic material and pore forming material
To remove pore forming material in high temperature furnace, high-temperature burner hearth atmosphere is air atmosphere, and high-temperature process temperature will not cause thermal barrier coating material
The phase transformation of material and sintering, and it is not result in that metallic matrix significantly aoxidizes.
The composite powder of thermal barrier coating ceramic material and pore forming material will be comprised in 600 DEG C～900 DEG C of air atmosphere,
Insulation 1h～20h.Specifically：First it is incubated 20h in 600 DEG C of air atmosphere, be then incubated in 700 DEG C of air atmosphere
10h, is finally incubated 5h in 800 DEG C of air atmosphere.
The invention also discloses a kind of porosity and the controlled thermal barrier coating of pore appearance, this thermal barrier coating is by containing thermal boundary
The composite powder of coating ceramic material and pore forming material after spraying thermal source heating, pile up in matrix surface and formed, should by collision
The porosity of thermal barrier coating is 5%～50%；And the inside particles of piling up in this thermal barrier coating are distributed with a diameter of 5～50 μm
The flat hole that subsphaeroidal hole and/or length are 10～50 μm, width is 0.3～10 μm.
The ratio of subsphaeroidal hole and flat hole and size can regulate and control.
Flat distribution of pores is in the hot-fluid vertical direction under this thermal barrier coating service state.
Thermal barrier coating ceramic material composite powder containing subsphaeroidal pore forming material is formed containing near by thermal spray deposition
The spraying particle of spherical void, the ceramic composite powder containing stratiform pore forming material is formed by thermal spraying and contains flat hole
Flaky particles, the long cross direction of flat hole and flaky particles be laminated consistent, vertical with the direction of heat flow of thermal barrier coating.
Compared with prior art, the present invention has following beneficial technique effect：
Porosity and the preparation method of the controlled thermal barrier coating of pore appearance that the present invention provides, prepare first containing thermal boundary
The composite powder of the pore forming material of coating ceramic material and different shape, is prepared containing pore forming material by hot spray process deposition
Volume fraction is 5%～50% composite coating, and pore forming material does not deform in thermal spray process, keeps original shape
Looks.By aoxidizing the pore forming material in burn off composite coating, thus obtaining identical with pore forming material pattern and position in the coating
Hole.The method is simple to operation, can be completed using existing thermal spraying apparatus spray deposited, will not produce raw material
Waste, and high-temperature oxidation to remove pore forming material simple and convenient, it is controlled etc. that prepared thermal barrier coating has pore structure, performance
Excellent effect, hole does not sinter in coating is on active service and is used, and can significantly be changed by adjusting porosity and pore appearance
The military service performance of kind thermal barrier coating and military service stability, are suitable to industrialized production and use.
Porosity and the controlled thermal barrier coating of pore structure that the present invention provides, wherein contain volume fraction for 5%～
50% hole；Comprise a diameter of 5～50 μm of spherical void and/or length is 10～50 μm, width is 0.3～10 μm flat
Flat-shaped hole.The porosity of this thermal barrier coating can significantly be regulated and controled, and the pattern of hole and size can also be effectively controlled,
Meanwhile, the performance of coating includes thermal conductivity, and elastic modelling quantity and fracture toughness all can be regulated and controled on a large scale, such that it is able to
To the Structure-Property Relationship design structure Thermal Barrier Coatings according to coating, effectively reduce the thermal conductivity of coating and improve coating
Service life, increase substantially the military service performance of thermal barrier coating, expand the range of application of thermal barrier coating so that the present invention carries
For thermal barrier coating can widely use in fields such as materials processing, Aero-Space, energy source and power, automobile making, shipbuildings.
Brief description
Fig. 1 is the composite powder of the 8YSZ and graphite prepared by spray drying method；Wherein, (a) is 70% volume fraction
8YSZ and 30% volume ratio spherical graphite；B () is the 8YSZ of 70% volume fraction and the lamellar graphite of 30% volume ratio；
Fig. 2 is the cross-section morphology of the porous 8YSZ coating obtaining after 800 DEG C of insulations remove graphite in 5 hours：Wherein, (a) is
The 8YSZ of 70% volume fraction is prepared with 30% volume ratio spherical graphite；(b) be 70% volume fraction 8YSZ with
30% volume ratio lamellar graphite prepares；
Fig. 3 is the graph of a relation in porous 8YSZ coating porosity and composite powder between graphite addition；
Fig. 4 is the cross-section morphology of the porous LZO coating obtaining after 900 DEG C of insulations remove graphite in 2 hours：Wherein, (a) is
The LZO of 85% volume fraction is prepared with 15% volume ratio spherical graphite；B () is the LZO and 15% of 85% volume fraction
Volume ratio lamellar graphite prepares.
Specific embodiment
With reference to specific embodiment, the present invention is described in further detail, described be explanation of the invention and
It is not to limit.
Porosity and the controlled thermal barrier coating of pore appearance that the present invention provides, if formed by heat barrier coat material powder
Xeothermic barrier material layer is constituted, barrier material interlayer be distributed with some laterally (thermal barrier coating in-plane) a diameter of 5～
50 μm of spherical void or length are 10～50 μm, and width is 0.3～10 μm of flat hole, the volume of pore forming material particle
Fraction is 5%～50%.The hole of flat the internal genesis analysis of thermal barrier coating by one layer to tens layers layer of thermal barrier material
In the thermal barrier coating of composition, the distribution of pores of flat is in the hot-fluid vertical direction under this thermal barrier coating service state.This heat
The thickness of barrier coating can be fabricated to 0.2～3mm according to different use occasions.
Porosity and the preparation method of the controlled thermal barrier coating of pore appearance that the present invention provides, comprise the steps of：
Step one, prepares the composite powder of thermal spraying material and pore forming material, composite powder is by warm by spray drying method
Barrier coating material and pore forming material composition, the volume fraction of pore forming material is 5%～50%, and remaining 50%～95% is thermal boundary painting
Layer material；Wherein the spheroidal particle of a size of a diameter of 5～50 μm of pore forming material and/or length are 10～50 μm, and width is 0.3
～10 μm of flat particle.
Step 2, by hot spray process, the composite powder comprising heat barrier coat material and pore forming material spraying is deposited on
On matrix, prepare containing volume fraction be 5%～50% pore forming material, remaining 50%～95% be heat barrier coat material
Composite ceramic coat, wherein, forms after pore forming material deposition and does not occur to melt or deform, thus keeping primary morphology, thermal boundary applies
Layer material fusing forms some flat granules, and flat granule forms layer of thermal barrier material in the way of being laminated on thickness direction,
Pore forming material particle is distributed between the flat granule that heat barrier coat material fusing is formed；
Step 3, by high-temperature oxidation, removes in composite ceramic coat by pore forming material, thus produces several in the coating
The spheroidal particle of what size and position and a diameter of 5～50 μm of above-mentioned pore forming material particle identical or length are 10～50 μm,
Width is 0.3～10 μm of flat particle, thus forming some flat granule stackings and being distributed between flat granule
Some a diameter of 5～50 μm of spheroidal particle or length are 10～50 μm, and width is the hole of 0.3～10 μm of flat particle
Structure and the controlled thermal barrier coating of pore appearance.
Wherein, hot spray process is plasma spraying.High-temperature oxidation is to put in high temperature furnace composite ceramic coat to go
Except pore forming material, wherein high-temperature process will not produce impact, only oxidation removal pore forming material to thermal barrier coating or matrix, concrete bag
Include in 600 DEG C of air atmosphere and be incubated 20 hours, in 700 DEG C of air atmosphere, be incubated 10 hours, in 800 DEG C of air atmosphere, insulation 5 is little
When.Pore forming material is the carbon simple substance that can be removed by high-temperature oxidation, specifically includes graphite, activated carbon.Heat barrier coat material
Powder includes zirconic acid lanthanum LZO powder, yttria-stabilized zirconia YSZ powder, lanthanum cerate LCO powder, lanthanum hexaaluminate powder and oxygen
Change aluminium powder.
The following is the specific embodiment of the preparation method of low heat conduction anti-sintering thermal barrier coating that the present invention provides, need explanation
, these embodiments are the present invention preferably examples, understand the present invention for those skilled in the art, but the present invention is not
It is confined to these embodiments.
Embodiment 1
The 8YSZ powder that step one is 50～100nm using particle diameter is 5 μm～50 μm as heat barrier coat material, particle diameter
Spherical graphite or length are 10～50 μm, and width is 0.3～10 μm of flat graphite as pore forming material, the wherein body of graphite
Fraction is the volume fraction of 30%, 8YSZ is 70%, prepares a size of 50～70 μm of composite powder by spray drying.
Step 2, using IN738 rustless steel be matrix, particle diameter be 50～70 μm composite powder as dusty spray, its
In middle composite powder, the volume fraction of pore forming material is 70% for 30%, 8YSZ volume fraction, and pore forming material is spherical for 5～50 μm
Graphite or length are 10～50 μm, and width is 0.3～10 μm of flat graphite.By plasma spraying, composite powder is sprayed
It is deposited on IN738 stainless steel base, obtain the 8YSZ composite ceramic coat that the volume fraction containing graphite is 30%.Graphite powder
Original pattern is kept, 8YSZ fusing forms some flat granules, and flat granule is to be laminated on thickness direction after the deposition of end
Mode form layer of thermal barrier material, graphite particle be distributed in 8YSZ powder fusing formed flat granule between.
Step 3, removes the 8YSZ composite ceramicses containing graphite particle in 5 hours by insulation in air atmosphere at 800 DEG C
Graphite in coating, obtains being 10～50 μm containing a diameter of 5～50 μm of spherical voids or length, width is 0.3～10 μm
The porosity of flat hole and the controlled thermal barrier coating of pore appearance.
The present embodiment be obtained composite powder fractography as shown in figure 1, wherein (a) be add volume ratio be 30%
Spherical graphite composite powder cross-section morphology, (b) be add volume ratio be 30% flat graphite composite powder break
Face pattern.From Fig. 1 (a), in prepared composite powder, there are spheroidal graphite particles, and coated by 8YSZ nanoparticle,
The diameter of spherical graphite is about 25 μm about.And as shown in Fig. 1 (b), as seen from the figure, in composite powder, contain a large amount of flat
Graphite, the length of flat graphite is 10～30 μm, and width is 1～5 μm.
The porosity of preparation and the controlled thermal barrier coating of pore appearance as shown in Fig. 2 wherein (a) be that body is contained by spraying
Fraction is the porous 8YSZ coating for preparing of composite powder of 30% spherical graphite, contains substantial amounts of ball in porous coating
Shape three-dimensional pore space, the porosity of coating is about 32%, and (b) is by spraying answering of the lamellar graphite being 30% containing volume fraction
Close the porous 8YSZ coating that powder prepares, contain substantial amounts of layered poros in coating, and layered poros are perpendicular to thick coating
Degree direction, the porosity of coating is about 25%.
Further, on the basis of embodiment 1, change the volume fraction of the powdered graphite adding, add volume respectively
Fraction is 0,10%, 20%, 30% powdered graphite, and the method preparation according to embodiment 1 is added with the 8YSZ of different porosities
Porous thermal barrier coating.Referring to Fig. 3, gained thermal barrier coating presents porosity therein and increases with increasing of graphite addition
Greatly.
Embodiment 2
As heat barrier coat material, particle diameter is 5 μm～50 μm balls to the LZO powder that step one is 50～100nm using particle diameter
Shape graphite or length are 10～50 μm, and width is 0.3～10 μm of flat graphite as pore forming material, the wherein volume of graphite
Fraction is the volume fraction of 15%, LZO is 85%, prepares a size of 50～70 μm of composite powder by spray drying.
Step 2, using IN738 be matrix, particle diameter be 50～70 μm composite powder as dusty spray, wherein compound
In powder the volume fraction of pore forming material be 15%, LZO volume fraction be 85%, pore forming material be 5～50 μm of spherical graphites or
Length is 10～50 μm, and width is 0.3～10 μm of flat graphite.By plasma spraying by spray deposited for composite powder
On IN738 matrix, obtain the LZO composite ceramic coat that the volume fraction containing graphite is 15%.Keep after powdered graphite deposition
Pattern originally, LZO fusing forms some flat granules, and flat granule forms thermal boundary in the way of being laminated on thickness direction
Material layer, graphite particle is distributed between the flat granule that the fusing of LZO powder is formed.
Step 3, removes the LZO composite ceramicses containing graphite particle in 2 hours by insulation in air atmosphere at 900 DEG C
Graphite in coating, obtains being 10～50 μm containing a diameter of 5～50 μm of spherical voids or length, width is 0.3～10 μm
The porosity of flat hole and the controlled thermal barrier coating of pore appearance.Referring to Fig. 4, it is after 900 DEG C of insulations remove graphite in 2 hours
The cross-section morphology of the porous LZO coating obtaining：The wherein LZO of (a) 85% volume fraction and the preparation of 15% volume ratio spherical graphite
The LZO of (b) obtaining 85% volume fraction is prepared with 15% volume ratio lamellar graphite.
Porosity that the present embodiment obtains and the controlled thermal barrier coating of pore appearance as shown in Fig. 2 wherein (a) be by spray
Apply the porous LZO coating that the composite powder of the spherical graphite being 15% containing volume fraction prepares, contain in porous coating
A certain amount of spherical three-dimensional pore space, the porosity of coating is about 19%, the layer that (b) is is 15% by spraying containing volume fraction
The porous LZO coating that the composite powder of shape graphite prepares, contains a certain amount of layered poros in coating, and layered poros hang down
Directly in coating layer thickness direction, the porosity of coating is about 17%.
Embodiment 3
, as heat barrier coat material, particle diameter is spherical for 5～50 μm for the LCO powder that step one is 50～100nm using particle diameter
Graphite or length are 10～50 μm, and width is 0.3～10 μm of flat graphite as pore forming material, the wherein volume integral of graphite
The volume fraction for 20%, LCO for the number is 80%, prepares a size of 50～70 μm of composite powder by spray drying.
Step 2, using IN738 be matrix, particle diameter be 50～70 μm composite powder as dusty spray, wherein compound
In powder the volume fraction of pore forming material be 20%, LCO volume fraction be 80%, pore forming material be 5～50 μm of spherical graphites or
Length is 10～50 μm, and width is 0.3～10 μm of flat graphite.By plasma spraying by spray deposited for composite powder
On IN738 matrix, obtain the LCO composite ceramic coat that the volume fraction containing graphite is 20%.Keep after powdered graphite deposition
Pattern originally, LCO fusing forms some flat granules, and flat granule forms thermal boundary in the way of being laminated on thickness direction
Material layer, graphite particle is distributed between the flat granule that the fusing of LCO powder is formed.
Step 3, removes the LCO composite ceramicses containing graphite particle in 5 hours by insulation in air atmosphere at 800 DEG C
Graphite in coating, obtains being 10～50 μm containing a diameter of 5～50 μm of spherical voids or length, width is 0.3～10 μm
The porosity of flat hole and the controlled thermal barrier coating of pore appearance.
Embodiment 4
Step one, the alumina powder being 50～100nm using particle diameter is 5～50 μm as heat barrier coat material, particle diameter
Spherical graphite or length are 10～50 μm, and width is 0.3～10 μm of flat graphite as pore forming material, the wherein body of graphite
Fraction is 30%, and the volume fraction of aluminium oxide is 70%, prepares a size of 50～70 μm of composite powder by spray drying.
Step 2, using IN738 be matrix, particle diameter be 50～70 μm composite powder as dusty spray, wherein compound
In powder, the volume fraction of pore forming material is 30%, and alumina body fraction is 70%, and pore forming material is 5～50 μm of spherical graphites
Or length is 10～50 μm, width is 0.3～10 μm of flat graphite.By plasma spraying, composite powder is spray deposited
On IN738 matrix, obtain the alumina composite ceramic coating that the volume fraction containing graphite is 30%.After powdered graphite deposition
Keep original pattern, aluminium oxide fusing forms some flat granules, and flat granule is in the way of being laminated on thickness direction
Form layer of thermal barrier material, graphite particle is distributed between the flat granule that alumina powder fusing is formed.
Step 3, removes the pottery of the alumina composite containing graphite particle for 5 hours by insulation in air atmosphere at 800 DEG C
Graphite in porcelain coating, obtains being 10～50 μm containing a diameter of 5～50 μm of spherical voids or length, width is 0.3～10 μm
The porosity of flat hole and the controlled thermal barrier coating of pore appearance.
Claims (9)
1. the preparation method of a kind of porosity and the controlled thermal barrier coating of pore appearance is it is characterised in that comprise the following steps：
1) pass through spray drying method, prepare the composite powder containing thermal barrier coating ceramic material and pore forming material, pore forming material exists
Volume fraction in composite powder is 5%～50%；
Wherein, pore forming material be the subsphaeroidal particle of 5～50 μm of diameter or 10～50 μm of length, 0.3～10 μm of width flat
One of shape material particle or two kinds；
2) pass through hot spray process, the composite powder comprising thermal barrier coating ceramic material and pore forming material is deposited on matrix；
3) pass through high-temperature oxidation, the pore forming material in burn off composite coating, obtain in the coating and pore forming material pattern and position
Put identical hole, that is, porosity and pore appearance controlled thermal barrier coating are obtained.
2. porosity according to claim 1 and the controlled thermal barrier coating of pore appearance preparation method it is characterised in that
Described pore forming material is the carbon simple substance that can be removed by high-temperature oxidation or high-melting-point Organic substance.
3. porosity according to claim 2 and the controlled thermal barrier coating of pore appearance preparation method it is characterised in that
Pore forming material is graphite or activated carbon.
4. porosity according to claim 1 and the controlled thermal barrier coating of pore appearance preparation method it is characterised in that
Thermal barrier coating ceramic material is zirconic acid lanthanum, lanthanum cerate, gadolinium zirconate, lanthanum hexaaluminate, aluminium oxide, yttria-stabilized zirconia or contains
The zirconium oxide of other oxide steady oxides.
5. porosity according to claim 1 and the controlled thermal barrier coating of pore appearance preparation method it is characterised in that
Step 2) described hot spray process adopt plasma spraying or plasma spraying complex phase deposition.
6. porosity according to claim 1 and the controlled thermal barrier coating of pore appearance preparation method it is characterised in that
Step 3) described high-temperature oxidation is 600 DEG C～900 by the composite powder comprising thermal barrier coating ceramic material and pore forming material
DEG C air atmosphere in, be incubated 1h～20h.
7. a kind of porosity and the controlled thermal barrier coating of pore appearance are it is characterised in that this thermal barrier coating is by containing thermal barrier coating
The composite powder of ceramic material and pore forming material after spraying thermal source heating, pile up in matrix surface and formed, this thermal boundary by collision
The porosity of coating is 5%～50%；And the inside particles of piling up in this thermal barrier coating are distributed with a diameter of 5～50 μm of nearly ball
The flat hole that shape hole and/or length are 10～50 μm, width is 0.3～10 μm.
8. porosity according to claim 7 and the controlled thermal barrier coating of pore appearance are it is characterised in that subsphaeroidal hole
And the ratio of flat hole and size can regulate and control.
9. porosity according to claim 7 and the controlled thermal barrier coating of pore appearance are it is characterised in that flat hole
It is distributed in the hot-fluid vertical direction under this thermal barrier coating service state.
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| CN108517484A (en) * | 2018-04-16 | 2018-09-11 | 西安工业大学 | A kind of dead-end pore structure ceramic coat and its preparation process |
| CN108530062A (en) * | 2018-05-14 | 2018-09-14 | 广东省新材料研究所 | A kind of superhigh temperature thermal barrier coating hollow structure powder and the preparation method and application thereof, superhigh temperature thermal barrier coating |
| CN110551963A (en) * | 2019-09-03 | 2019-12-10 | 哈尔滨工程大学 | Material and method for porosity regulation and strength supplement of thermal barrier coating |
| CN110643930A (en) * | 2019-11-15 | 2020-01-03 | 河北工业大学 | Preparation method of composite thermal barrier coating resistant to high temperature CMAS and rainwater corrosion |
| CN115260867A (en) * | 2022-07-06 | 2022-11-01 | 中城国网(北京)综合能源有限公司 | Long-acting anti-condensation polymer nano thermal insulation coating and preparation method thereof |
| JP7516293B2 (en) | 2021-03-03 | 2024-07-16 | 株式会社東芝 | Heat-resistant components and power generation systems |
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| CN107473739A (en) * | 2017-09-08 | 2017-12-15 | 中国人民解放军国防科技大学 | lanthanum zirconate complex phase ceramic and preparation method and application thereof |
| CN108517484A (en) * | 2018-04-16 | 2018-09-11 | 西安工业大学 | A kind of dead-end pore structure ceramic coat and its preparation process |
| CN108517484B (en) * | 2018-04-16 | 2020-12-18 | 西安工业大学 | Ceramic coating with closed pore structure and preparation process thereof |
| CN108530062A (en) * | 2018-05-14 | 2018-09-14 | 广东省新材料研究所 | A kind of superhigh temperature thermal barrier coating hollow structure powder and the preparation method and application thereof, superhigh temperature thermal barrier coating |
| CN110551963A (en) * | 2019-09-03 | 2019-12-10 | 哈尔滨工程大学 | Material and method for porosity regulation and strength supplement of thermal barrier coating |
| CN110551963B (en) * | 2019-09-03 | 2021-06-01 | 哈尔滨工程大学 | Material and method for porosity regulation and strength supplement of thermal barrier coating |
| CN110643930A (en) * | 2019-11-15 | 2020-01-03 | 河北工业大学 | Preparation method of composite thermal barrier coating resistant to high temperature CMAS and rainwater corrosion |
| JP7516293B2 (en) | 2021-03-03 | 2024-07-16 | 株式会社東芝 | Heat-resistant components and power generation systems |
| CN115260867A (en) * | 2022-07-06 | 2022-11-01 | 中城国网(北京)综合能源有限公司 | Long-acting anti-condensation polymer nano thermal insulation coating and preparation method thereof |
| CN115260867B (en) * | 2022-07-06 | 2023-10-13 | 中城国网(北京)综合能源有限公司 | Long-acting anti-dewing high-molecular nano heat-insulating coating and preparation method thereof |
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